Gas turbine engine component having bypass circuit

ABSTRACT

A gas turbine engine component has an annular flange arm, a backing plate mounted to the flange arm and a bypass circuit formed between the flange arm and the backing plate. The bypass circuit includes one or more channels formed in one of the flange arm or the backing plate. When more than one channels are used, at least one connecting slot is provided between the channels. At least one inlet passage extends through the flange arm in fluid communication with the forward-most channel, and at least one outlet slot is formed between the flange arm and the backing plate in fluid communication with the aft-most channel.

BACKGROUND OF THE INVENTION

This invention relates generally to gas turbine engines and moreparticularly to seal bypass circuits in such engines.

A gas turbine engine includes a compressor that provides pressurized airto a combustor wherein the air is mixed with fuel and ignited forgenerating hot combustion gases. These gases flow downstream to one ormore turbines that extract energy therefrom to power the compressor andprovide useful work such as powering an aircraft in flight. Aircraftengines ordinarily include a stationary turbine nozzle disposed at theoutlet of the combustor for channeling combustion gases into the firststage turbine rotor disposed downstream thereof. The turbine nozzledirects the combustion gases in such a manner that the turbine bladescan do work.

Because they are exposed to intense heat generated by the combustionprocess, certain components, such as combustor liners and turbine rotorblades and nozzles, are cooled to meet life expectancy requirements.This cooling is commonly accomplished with relatively cool air that isdiverted from the compressor discharge. Typically, a forward outer sealis provided between the stationary turbine nozzle and the first stageturbine rotor for sealing the compressor discharge air that is bled offfor cooling purposes from the hot gases in the turbine flow path.Conventional forward outer seals comprise a rotating labyrinth seal madeup of a rotating member and a static member that are generally situatedcircumferentially about the longitudinal centerline axis of the engine.The static member includes an annular flange to which a stator elementis mounted. The stator element is normally made of a honeycomb material.The rotating member has a number of thin, tooth-like projectionsextending radially toward the stator element. The outer circumference ofeach projection rotates within a small tolerance of the stator element,thereby effecting sealing between the cooling air and the hot gases inthe turbine flow path.

During engine operation, certain engine structure does not heat up asfast as other structure because of differences in mass and the degree ofexposure to the hot gases. This effect results in radial thermalgradients in many engine components, such as the static member in whichthe annular flange does not heat up as fast as other portions of themember. Thermal gradients in the static member can cause high thermalstresses and improper seal clearance between the stator element and therotating tooth-like projections. To reduce the thermal gradient of theflange, it is known to provide a flange bypass circuit through whichsome of the compressor discharge air bled off for cooling purposespasses. Although this air is cooler than the hot gas flow, it is warmenough to provide faster heating of the flange. The faster heatingresults in a smaller thermal gradient. Conventional bypass circuitsutilize a series of discrete circuits spaced along the circumference ofthe flange and the stator element's backing plate. This discrete circuitarrangement provides non-uniform heating of the flange, requireselaborate machining, and uses small fillet radii that create stressconcentrations.

Accordingly, there is a need for a bypass circuit that would providemore uniform heating of the flange and allow simpler machining.

SUMMARY OF THE INVENTION

The above-mentioned need is met by the present invention, which, in oneembodiment, provides a gas turbine engine component having a bypasscircuit formed in the inner surface of an annular flange arm. The bypasscircuit includes a channel formed in the radially inner surface. Atleast one inlet passage extends radially through the flange arm in fluidcommunication with the channel, and at least one outlet slot is formedin the radially inner surface in fluid communication with the channel.

In another embodiment, the present invention provides a gas turbineengine component including an annular flange arm having a radially innersurface and an annular backing plate mounted to the radially innersurface, the backing plate having a radially outer surface. A bypasscircuit includes a channel formed in the radially outer surface of thebacking plate. At least one inlet passage extends radially through theflange arm in fluid communication with the channel, and at least oneoutlet slot is formed in the radially outer surface in fluidcommunication with the channel.

In yet another embodiment, the gas turbine engine component includes anannular flange arm having a radially inner surface, a radially outersurface, a forward end and an aft end defining an aft edge. First andsecond channels are formed in the radially inner surface, with thesecond channel being spaced axially from the first channel. A pluralityof connecting slots is formed in the radially inner surface; each one ofthe connecting slots extends axially between the first and secondchannels. A plurality of inlet passages extends radially through theflange from the radially outer surface to the first channel. A pluralityof outlet slots is formed in the radially inner surface, with eachoutlet slot extending axially from the second channel to the aft edge.

The present invention and its advantages over the prior art will be morereadily understood upon reading the following detailed description andthe appended claims with reference to the accompanying drawings.

DESCRIPTION OF THE DRAWINGS

The subject matter that is regarded as the invention is particularlypointed out and distinctly claimed in the concluding part of thespecification. The invention, however, may be best understood byreference to the following description taken in conjunction with theaccompanying drawing figures in which:

FIG. 1 is a schematic, longitudinal cross-sectional view of a gasturbine engine.

FIG. 2 is a partial cross-sectional view of the high pressure turbinesection of the gas turbine engine of FIG. 1.

FIG. 3 is an enlarged, partial cross-sectional view (taken along line3—3 of FIG. 4) showing the forward outer seal from the high pressureturbine section of FIG. 2 in more detail.

FIG. 4 is a partial, radial plan view of the radially outer surface ofthe flange arm from the forward outer seal of FIG. 3.

FIG. 5 is a partial, aft-looking-forward end view of the flange arm fromthe forward outer seal of FIG. 3.

FIG. 6 is an enlarged, partial cross-sectional view (taken along line6—6 of FIG. 7) showing a second embodiment of a forward outer seal for ahigh pressure turbine section.

FIG. 7 is a partial, radial plan view of the radially outer surface ofthe backing plate from the forward outer seal of FIG. 6.

FIG. 8 is a partial, aft-looking-forward end view of the backing platefrom the forward outer seal of FIG. 6.

DETAILED DESCRIPTION OF THE INVENTION

Referring to the drawings wherein identical reference numerals denotethe same elements throughout the various views, FIG. 1 schematicallyshows an exemplary turbofan gas turbine engine 10. While turbofanengines in general are well known in the art, a brief description of theoverall configuration of the engine 10 and the interrelationship of itsvarious components will enhance understanding of the invention to bedescribed below. Furthermore, it should be pointed out that a turbofanengine is used only as an example; the present invention is not limitedto turbofan engines and can be implemented in a wide variety of enginetypes as well as other applications.

The engine 10 includes, in serial axial flow communication about alongitudinal centerline axis 12, a fan 14, booster 16, high pressurecompressor 18, combustor 20, high pressure turbine 22, and low pressureturbine 24. The high pressure turbine 22 is drivingly connected to thehigh pressure compressor 18 with a first rotor shaft 26, and the lowpressure turbine 24 is drivingly connected to both the booster 16 andthe fan 14 with a second rotor shaft 28. The fan 14 comprises aplurality of radially extending fan blades 30 mounted on an annular disk32, wherein the disk 32 and the blades 30 are rotatable about thelongitudinal centerline axis 12 of engine 10.

During operation of engine 10, ambient air 34 enters the engine inletand a first portion of the ambient air 34, denoted the primary gasstream 36, passes through the fan 14, booster 16 and high pressurecompressor 18, being pressurized by each component in succession. Theprimary gas stream 36 then enters the combustor 20 where the pressurizedair is mixed with fuel and burned to provide a high energy stream of hotcombustion gases. The high energy gas stream passes through the highpressure turbine 22 where it is expanded, with energy extracted to drivethe high pressure compressor 18, and then the low pressure turbine 24where it is further expanded, with energy being extracted to drive thefan 14 and the booster 16. A second portion of the ambient air 34,denoted the secondary or bypass airflow 38, passes through the fan 14and the fan outlet guide vanes 40 before exiting the engine through anannular duct 42, wherein the secondary airflow 38 provides a significantportion of the engine thrust.

Referring to FIG. 2, there is shown a partial view of the high pressureturbine 22. The high pressure turbine 22 includes a turbine nozzleassembly 44 and a first stage turbine rotor (not shown in FIG. 2)located aft or downstream of the turbine nozzle assembly 44. The turbinenozzle assembly 44 and the turbine rotor are spaced axially to define aforward wheel cavity 45 therebetween (i.e., immediately forward of theturbine rotor). The forward wheel cavity 45 is in fluid communicationwith the turbine flow path through which the hot combustion gases flow.

The turbine nozzle assembly 44 includes an inner nozzle support 46 towhich a plurality of circumferentially adjoining nozzle segments 48 ismounted. The nozzle segments 48 collectively form a complete 3600assembly. Each segment 48 has two or more circumferentially spaced vanes50 (one shown in FIG. 2) over which the combustion gases flow. The vanes50 are configured so as to optimally direct the combustion gases to thefirst stage turbine rotor. The inner nozzle support 46 is a stationarymember suitably supported in the engine 10 and has a substantiallyconical configuration. The nozzle segments 48 are mounted to the axiallyand radially distal end of the inner nozzle support 46. The turbinenozzle assembly 44 also includes a stationary member 52 fastened to aninwardly extending flange 53 formed on the inner nozzle support 46, nearthe axially and radially distal end thereof. Although shown as aseparate piece, the stationary member 52 could alternatively beintegrally formed with the inner nozzle support 46. The inner nozzlesupport 46 and the stationary member 52 define a chamber 54 locatedaxially therebetween.

The stationary member 52 is a generally annular structure having anouter flange 56, and inner flange 58 and an inducer 60 radially disposedbetween the outer flange 56 and the inner flange 58. The outer flange 56is formed on a flange arm 61 that is annular in configuration anddefines an axially extending, substantially cylindrical surface. Asrepresented by arrow A in FIG. 2, cooling air (typically air divertedfrom the compressor 18) passes through a series of air holes 62 formedin the inner nozzle support 46 into the chamber 54. The inducer 60accelerates and directs some of this air tangentially toward the turbinerotor located aft of the turbine nozzle assembly 44. The inducer 60typically comprises a circumferentially disposed array of vanes thatcontrols the tangential speed and direction of the airflow so that it issubstantially equal to that of the turbine rotor.

The engine 10 further includes an annular rotating member 64 fixed forrotation with the turbine rotor. The rotating member 64 contacts thestationary member 52 to form a forward outer seal 66 for sealingcompressor discharge air bled off for cooling purposes from the hotgases in the turbine flow path. Preferably, the forward outer seal 66 isa rotating labyrinth seal that includes a number of thin, tooth-likeprojections 68 attached to, or integrally formed on, the rotating member64. The projections 68 are annular members that extend radially outwardtoward the flange arm 61. The labyrinth seal 66 further includes anannular stator element 70 attached to the flange arm 61 and positionedradially outward of and circumferentially about the projections 68.

Turning now to FIG. 3, the radially outer surface of the stator element70 is mounted to the flange arm 61 via an annular backing plate 71. Theradially inner surface of the stator element 70 is tiered. Each one ofthe projections 68 is axially aligned with a corresponding tier of thestator element 70. By “axially aligned,” it is meant that eachprojection 68 is located along the axial direction between the forwardand aft edges of the corresponding tier. The outer circumference of eachprojection 68 rotates within a small tolerance of the correspondinginner circumference of the stator element 70, thereby effecting sealingbetween the cooling air and the hot gases in the turbine flow path. Thestator element 70 is preferably made of a honeycomb material to reducefriction and subsequent heat generation during operation. Although FIG.2 shows three of the projections 68, it should be noted that the presentinvention is not limited to three; more or fewer than three projectionscan be used.

Referring to FIGS. 3–5 a bypass circuit 72 is illustrated. The bypasscircuit 72 provides for the flow of air from the chamber 54 to theforward wheel cavity 45, thereby providing faster heating of the flangearm 61 and the outer flange 56 and reducing the thermal gradientthereof. The airflow through the bypass circuit 72 also purges theforward wheel cavity 45 so as to prevent hot gas ingestion. In theillustrated embodiment, the bypass circuit 72 comprises first and secondchannels 74 and 76 formed in the radially inner surface 78 of the flangearm 61, which is the surface to which the backing plate 71 is mounted.Both of the first and second channels 74 and 76 extend around the entirecircumference of the flange arm 61 to define continuous ring channels.The channels 74 and 76 are spaced axially with the first channel 74being located near the forward end of the flange arm 61, and the secondchannel 76 being located near the aft end of the flange arm 61. Thebypass circuit 72 further includes a plurality of connecting slots 80formed in the radially inner surface 78 and equally spaced about thecircumference of the flange arm 61. The connecting slots 80 extendaxially between the first and second channels 74 and 76 to allow air toflow from the first channel 74 to the second channel 76.

The bypass circuit 72 further includes a plurality of inlet passages 82equally spaced about the circumference of the flange arm 61. Each inletpassage 82 extends radially through the flange arm 61 from an inlet port84 formed on the radially outer surface 86 of the flange arm 61 to thefirst channel 74. The inlet passages 82 thus provide fluid communicationbetween the chamber 54 and the first channel 74. The inlet passagescould alternatively have a non-radial orientation as long as theyprovided fluid communication between the chamber 54 and the firstchannel 74. The number and size of the inlet passages 82 are selected toprovide a significant contribution to control the desired amount ofairflow through the bypass circuit 72. A plurality of outlet slots 88 isformed in the radially inner surface 78 and equally spaced about thecircumference of the flange arm 61. Each outlet slot 88 extends axiallyfrom the second channel 76 to the aft end of the flange arm 61 to definean outlet port 90 in the aft facing edge 92 of the flange arm 61. Theoutlet slots 88 are thus in fluid communication with the first channel74 via the second channel 76 and the connecting slots 80. Although theycan be substantially parallel to the centerline axis 12, the outletslots 88, as well as the connecting slots 80, are preferably angled in acircumferential direction to minimize flow-turning losses and pre-swirlthe cavity purge air to reduce cavity windage and absolute airtemperature.

It should be noted that the present invention is not limited to two ringchannels. Additional ring channels, and corresponding additional sets ofconnecting slots, could be utilized. Furthermore, the bypass circuitcould be configured with a single ring channel. In this case, aplurality of inlet passages would be formed in the flange arm in fluidcommunication with the single ring channel. A plurality of outlet slotswould be formed in the flange arm so as to extend from the single ringchannel to the aft end of the flange arm. Connecting slots would not berequired in this embodiment.

The configuration of the bypass circuit simplifies machining relative toconventional bypass circuits. Specifically, the two circumferentialchannels 74 and 76 can be turned on a lathe, and the angled connectingslots 80 and outlet slots 88 can be milled with a ball mill. Thisprovides a large fillet radius that minimizes stress concentrations inthe flange arm 61. Generally, the connecting slots 80 and outlet slots88 define fillet radii that are greater than the slot depth. In oneembodiment, slot fillet radii are approximately 3–4 times greater thanthe slot depth. After the bypass circuit 72 is machined, the backingplate 71 is mounted to the radially inner surface 78 so as to cover thefirst and second channels 74 and 76, the connecting slots 80 and theoutlet slots 88.

During engine operation, air from the chamber 54 enters the bypasscircuit 72 via the inlet ports 84. The air passes through the inletpassages 82 to the first channel 74. Air then passes from the firstchannel 74 to the second channel 76 via the connecting slots 80. Fromthe second channel 76, the air flows through the outlet slots 88 andexits the bypass circuit 72 through the outlet ports 90 into the forwardwheel cavity 45. The geometry of the bypass circuit 72 provides a moreuniform distribution of the relatively hot air to heat the flange arm 61and the outer flange 56 evenly.

Referring to FIGS. 6–8, an alternative embodiment of a bypass circuit172 is illustrated. In the this embodiment, the bypass circuit 172comprises first and second channels 174 and 176 formed in the radiallyouter surface 179 of the backing plate 171, which is the surface that ismounted to the flange arm 161. Both of the first and second channels 174and 176 extend around the entire circumference of the backing plate 171to define continuous ring channels. The channels 174 and 176 are spacedaxially with the first channel 174 being located near the forward end ofthe backing plate 171, and the second channel 176 being located near theaft end of the backing plate 171. The bypass circuit 172 furtherincludes a plurality of connecting slots 180 formed in the radiallyouter surface 179 and equally spaced about the circumference of thebacking plate 171. The connecting slots 180 extend axially between thefirst and second channels 174 and 176 to allow air to flow from thefirst channel 174 to the second channel 176.

The bypass circuit 172 further includes a plurality of inlet passages182 equally spaced about the circumference of the flange arm 161. Eachinlet passage 182 extends radially through the flange arm 161 from aninlet port 184 formed on the radially outer surface 186 of the flangearm 161 to the first channel 174. A plurality of outlet slots 188 isformed in the radially outer surface 179 and equally spaced about thecircumference of the backing plate 171. Each outlet slot 188 extendsaxially from the second channel 176 to the aft end of the backing plate171 to define an outlet port 190 in the aft facing edge of the backingplate 171. The outlet slots 188 are thus in fluid communication with thefirst channel 174 via the second channel 176 and the connecting slots180. As with the first embodiment, it should be noted that thisembodiment is not limited to two ring channels. Additional ringchannels, and corresponding additional sets of connecting slots, couldbe utilized. Furthermore, the bypass circuit could be configured withjust a single ring channel.

While specific embodiments of the present invention have been described,it will be apparent to those skilled in the art that variousmodifications thereto can be made without departing from the spirit andscope of the invention as defined in the appended claims.

1. A gas turbine engine component comprising: an annular flange armhaving a radially inner surface; a first channel formed in said radiallyinner surface; at least one inlet passage extending through said flangearm in fluid communication with said first channel; and at least oneoutlet slot formed in said radially inner surface in fluid communicationwith said first channel.
 2. The component of claim 1 further comprising:a second channel formed in said radially inner surface, said secondchannel being spaced axially from said first channel; and at least oneconnecting slot formed in said radially inner surface and extendingbetween said first and second channels, wherein said outlet slot extendsaxially from said second channel.
 3. The component of claim 2 whereinsaid first and second channels circumferentially extend entirely aroundsaid flange arm.
 4. The component of claim 2 wherein said first channelis located forward of said second channel.
 5. The component of claim 2wherein said connecting slot and said outlet slot are angled in acircumferential direction.
 6. The component of claim 2 wherein saidconnecting slot and said outlet slot each define a depth and a filletradius that is greater than said depth.
 7. A gas turbine enginecomponent comprising: an annular flange arm having a radially innersurface, a radially outer surface, a forward end and an aft end definingan aft edge; a first channel formed in said radially inner surface; asecond channel formed in said radially inner surface, said secondchannel being spaced axially from said first channel; a plurality ofconnecting slots formed in said radially inner surface, each one of saidconnecting slots extending axially between said first and secondchannels; a plurality of inlet passages extending through said flangearm from said radially outer surface to said first channel; and aplurality of outlet slots formed in said radially inner surface, eachone of said outlet slots extending axially from said second channel tosaid aft edge.
 8. The component of claim 7 wherein said first and secondchannels circumferentially extend entirely around said flange arm. 9.The component of claim 7 wherein said first channel is located near saidforward end and said second channel is located near said aft end. 10.The component of claim 7 wherein each one of said outlet slots definesan outlet port in said aft edge.
 11. The component of claim 7 whereinsaid connecting slots and said outlet slots are angled in acircumferential direction.
 12. The component of claim 7 wherein each oneof said connecting slots and each one of said outlet slots define adepth and a fillet radius that is greater than said depth.
 13. Thecomponent of claim 7 wherein said connecting slots are equally spacedabout said flange arm.
 14. The component of claim 7 wherein said inletpassages are equally spaced about said flange arm.
 15. The component ofclaim 7 wherein said outlet slots are equally spaced about said flangearm.